CN107429573A

CN107429573A - Turbine components thermal barrier coating with vertically-aligned design surface and more bifurcated cavity features

Info

Publication number: CN107429573A
Application number: CN201580076436.1A
Authority: CN
Inventors: K.卡道; J.A.帕斯夸尔-古铁雷斯; A.沙马
Original assignee: Siemens AG
Current assignee: Siemens AG
Priority date: 2014-02-25
Filing date: 2015-12-08
Publication date: 2017-12-01
Also published as: WO2015130519A1; RU2016137796A; RU2016134446A; CN108699916A; JP2018507988A; WO2015130527A3; US10189082B2; CN106030043B; WO2015130526A3; US20190048730A1; EP3111049A1; EP3397840A1; EP3111048A2; WO2015130521A2; RU2016137904A; CN106030040A; WO2015130526A2; CN107250485A; CN107250485B; WO2015130521A3

Abstract

The invention discloses a kind of turbogenerator（80）Part, such as, blade（92）, stator blade（104、106）, ring segment 110, wearing face 120 or transition piece（85）, the turbine engine components have vertically-aligned design surface feature（ESFs）（632、634）With the design cavity feature of bifurcated（EGFs）（642、652）.EGF（642、652）Plane configuration pattern be cut to the thermal barrier coating of part（TBC）Outer surface in.EGF patterns include the correspondingly corresponding ESF with lower section（632、634）Vertically-aligned overlying summit（644）Plane configuration pattern.EGF（640）At least three interior corresponding groove sections（642、652、642）Each respective vertices are focused at the pattern of more bifurcateds（644）Place so that with stress（σ_A）In each continuous summit connecting portion punishment fork（σ_B、σ_C）, the stress of caused crackle decays in cascaded fashion.

Description

Turbine components thermal boundary with vertically-aligned design surface and more bifurcated cavity features Coating

The cross reference of prioity claim and related application

This application claims the priority under following international patent application, and the full content of each of which is by reference It is incorporated herein：

On 2 18th, 2015 Application No. PCT/US2015/016318 submit, distribution " TURBINE COMPONENT THERMAL BARRIER COATING WITH CRACK ISOLATING ENGINEERED GROOVE FEATURES”；And

On 2 18th, 2015 Application No. PCT/US2015/016331 submit, distribution " TURBINE COMPONENT THERMAL BARRIER COATING WITH CRACK ISOLATING ENGINEERED SURFACE FEATURES”。

Docket Number is 2015P17004WO and the sequence number distributed（It is unknown）Entitled " TURBINE COMPONENT THERMAL BARRIER COATING WITH CRACK ISOLATING, CASCADING, The international patent application submitted while MULTIFURCATED ENGINEERED GROOVE FEATURES " is considered as related Shen Please and it be incorporated herein by reference.

Technical field

The present invention relates to the working fluid at it exposed to heating（Such as, burning gases or high steam）Part table Face（Such as, blade, stator blade, ring segment or transition piece）It is upper that there is thermal barrier coating（“TBC”）Burning or steamturbine hair Motivation, it includes each subassembly comprising these thermal barrier coatings.The invention further relates to generally followed for reducing by engine thermal Ring or foreign object damage（“FOD”）The Crack Extension of these caused part TBC layers or the method for spalling damage.More specifically Ground, various embodiments described herein are related to：The more bifurcated cavity features of design in TBC outer surface（“EGF”）Plane The formation of form pattern, the more bifurcated cavity features of the design（“EGF”）With the design surface feature projected upwards from part（“ESF”） It is vertically-aligned.EGF includes the plane configuration pattern on overlying summit, and the overlying summit is correspondingly right vertically with the corresponding ESF of lower section It is accurate.At least three corresponding groove sections in EGF patterns are focused at each corresponding overlying apex in the form of more bifurcateds so that every The groove section of individual convergence each overlying apex have at least two other（That is, bifurcated）Adjacent convergent channel section.It is vertical right Accurate ESF and the EGF of bifurcated make the thermal stress in TBC or foreign object damage（FOD）Caused Crack Extension is limited to part, otherwise The Crack Extension may allow excessive TBC to peel off and then damaged to the heat exposure of turbine part lower substrate.

Background technology

Known turbogenerator（Including gas/combustion turbine engine and steam turbine engines）Comprising by turbine The axle mount type turbine blade that shell or housing circumferentially surround.Although the remainder of this specification focuses on combustion Burn or Gas turbine technology apply and environment in application on, but exemplary embodiment described herein is applicable to Steam turbine engines.In combustion gas/combustion turbine engine, hot combustion gas flow into the combustion path originated in burner And it is directed to by the transition piece of generally tubulose in turbine.Forward or the 1st row's stator blade guides burning gases By multiple rows of continuous alternately turbine blade and stator blade.The hot combustion gas for hitting turbine blade cause blade to rotate, so as to Heat energy in hot gas is converted into mechanical work, the mechanical work can be used for rotating machinery（Such as, generator）Power is provided.

Engine interior part in hot combustion gas path is exposed to about more than 1000 degrees Celsius（1832 Fahrenheits Degree）Ignition temperature under.Engine interior part in combustion path（Such as, for example, burning block transition piece, stator blade and Blade）Typically constructed by high temperature resistant superalloy.Blade and stator blade generally include to terminate in the Cooling Holes in member outer surface Cooling duct, to make coolant fluid pass through into combustion path.

Turbogenerator internal part generally comprises thermal boundary coating or the coating of cermet material（“TBC”）, the heat Barrier coating or coating（“TBC”）It is applied directly to the outer surface of part substrate or had previously been coated to the centre of substrate surface Metal combination coating（“BC”）On.TBC provides thermal insulation layer on part substrate, and this reduces substrate temperature.TBC is applied and part In the combination of cooling duct further reduce substrate temperature.In some applications, multilayer TBC has been used, in this case, Outer surface is referred to herein as outside thermal barrier coating exposed to the outermost TBC layer of burning gases（“OTBC”）.When mention it is close with During the general material character of the coating of the coating outer surface of the hot working gas contact in engine, term " TBC " and " OTBC " Convertibly use herein.When mentioning the outer surface contacted with hot working gas, it will be TBC in monolayer embodiment Outer surface, or correspondingly in multiple layer embodiment by be OTBC outer surface.

Due to for the typical metal ceramics TBC material for manufacturing aforementioned exemplary turbine components and typical superalloy material Between difference on thermal expansion, fracture toughness and modulus of elasticity etc., so existing in the interface of foreign material produces TBC layer Heat causes stress and/or the mechanical potential risk for causing stress cracking and the loss of TBC/ turbine components adhesion strength.Crackle And/or adhesion strength loss/layering can negatively influence the structural intergrity of TBC layer, and potentially result in peeling（That is, TBC is made Insulating materials separates with turbine components）.For example, the vertical crack formed in TBC layer can extend to TBC/ substrate interfaces, And then horizontal proliferation.Similarly, the crackle of horizontal orientation can originate from TBC layer or close to TBC/ substrate interfaces. This rupture loss of TBC structural intergrities can cause the further premature harm to lower part substrate.When TBC layer departs from During lower substrate, substrate can lose its protective thermosphere coating.During the continuing to run with of turbogenerator, pushing away over time Move, hot combustion gas may corrode or if not damage exposed part substrate surfaces, start so as to potentially reduce Machine runs service life.Generated electricity online in the increased loading demand of power network and when making engine response as network load needs Ask reduction and it is idle when, potential peel off risk as continuous power on/off circulation can increase.Wind is peeled off in order to manage TBC Dangerous and other engine operation maintenance need, and generally can stop using combustion after the power on/off thermal cycle of predefined quantity Turbogenerator is burnt to carry out examination and maintenance.

Except be prone to thermally-induced stress or vibration cause stress cracking in addition to, the TBC layer on engine components exists When hitting more frangible TBC material foreign object damage also easily occurs for the contaminant particle in hot burning gas body（“FOD”）.Foreign matter rushes Hitting may crack TBC surfaces, finally cause the peeling of the surface integrity similar with road hollow to be lost.It is once different Thing impact makes the part peeling of TBC layer, and remaining TBC material is prone to the structural Crack Extension of insulating barrier and/or enters one Step is peeled off.In addition to the environmental damage of the TBC layer as caused by foreign matter, the pollutant in burning gases（Such as, calcium, magnesium, aluminium and Silicon（Commonly referred to as " CMAS "））TBC layer outer surface can be adhered to or reacted with TBC layer outer surface, so as to increase TBC The possibility of peeling and make lower section BC be exposed.

In order to improve TBC layer structural intergrity and fixation with turbine components lower substrate, the trial that the past is made is Through including the research and development of the stronger TBC material to can more resist thermal fracture or FOD, but the cost paid is thermal resistivity drop The increase of low or material cost.Be commonly used for TBC coating relatively strong, less frangible potential material have it is relatively low Thermal resistivity.Alternately, as trading off, the multilayer TBC material with different favorable properties individually applied is applied to Turbine components substrate, for example, the more fragile or more soft TBC material with more preferable insulating property (properties), its again by it is stronger, Low insulation value TBC material covering using as can more resist FOD and/or CMAS or other chemical contaminations adhesion it is harder " armor " external coating.In order to improve the TBC adhesion strengths with lower substrate, directly by intermetallic metal combination coating（BC）Coating On substrate.Also from smooth exposed surface have modified to TBC substrate or BC interfaces body structure surface property and/ Or configuration.Some known substrate and/or BC surface modifications（For example, so-called " coarse combination coating " or RBC）Wrap Included makes surface roughening by ablation or other injections, thermal spray deposition etc..In some cases, to BC or base It is about several microns that plate surface, which has carried out photoresist or laser-induced thermal etching to include height and spacing width in configuration of surface, （μm）Surface characteristics.Feature is directly formed on the substrate surface of turbine blade tip to apply to alleviate vane tip The stress that layer is subjected to.Thermal spraying has been carried out to coarse combination coating to leave the porous table of the feature of several microns of sizes Face.By partly changing the homogeney of coated ceramic metallic material, TBC layer has been coated with to create pre weakened method Area on controlled direction to attract Crack Extension.For example, corresponding with known or possible area of stress concentration Weakening region is created in TBC layer, so that any crackle formed in the weakening region extends to minimize in the desired direction The overall structure of TBC layer is damaged.

The content of the invention

Each embodiment of turbine components construction described herein and the method for making turbine components helps In the protection turbine components thermal barrier coating during turbine engine operates（“TBC”）Structural intergrity.In some embodiments In, it is formed directly into part substrate or coated in the design surface feature in the intermediate layer on substrate（ESF）Improve TBC layer is to its adhesion strength.In certain embodiments, ESF is used as the wall or screen for the crackle that containment is either isolated in TBC layer Barrier, so as to suppress the additional Crack Extension in this layer or the layering with adjacent context layer.In certain embodiments, ESF It is vertically aligned with the summit for assembling EGF.

In certain embodiments, cavity feature is designed（EGF）Cutting and formation enter it in TBC layer and by its outer surface In the TBC layer of preceding formation, such as, pass through laser, water spray or machining.Diffused through as fire is prevented in combustible material The EGF of the equivalent of the fire line in space or gap prevents the crackle in TBC layer from further expanding by the groove so as to reach Other regions in TBC layer.In certain embodiments, stressed zones pair of the EGF with being easily formed crackle during power operation It is accurate.In these embodiments, groove is formed in stressed zone and removes during power operation that may or perhaps can be formed should The material of power crackle.In other embodiments, EGF is formed in a manner of convenient two dimension or polygon plane form pattern In TBC layer.EGF makes thermal stress or foreign object damage in TBC（FOD）Caused Crack Extension localizes, otherwise the crackle Extension may allow excessive TBC to peel off and then damaged to the heat exposure of turbine components lower substrate.It will be formed The given TBC surface areas of one or more stress crackings separate with the non-broken portion outside EGF.Therefore, if by one Or the broken portion that multiple EGF keep apart peels off from the part, then due to the crackle contained, so outside the crackle comprising groove Remaining TBC surfaces will not peel off.

In certain embodiments, the peeling for the rupture TBC material being constrained in ESF and/or EGF can leave cheats with road Hollow similar beneath portions TBC layer.Form the bottom surface of " hollow " or the lower section TBC material of basic unit is narrow for turbine engine components Stitch substrate and lasting Thermal protection is provided.

In certain embodiments, ESF has the plane configuration pattern for the more bifurcated groove sections assembled in summit.More bifurcateds Groove geometry is useful for preventing the Crack Extension in TBC, and no matter the stress for causing crackle in TBC is by heat-machine Caused by tool stress or as caused by heating transient state or it is by foreign object damage（FOD）Caused by impulse machine stress.Rise Start from the border of any single polygon defined by ESF grooves and cause the stress of crackle by by the TBC in peripheral polygon Material volume dissipates（That is, it is stopped in wherein）, or crackle caused by stress in TBC material most at last with peripheral polygon One or more of border groove section intersect, one or more groove sections are in public shared apex and other downstream ESF grooves Duan Huiju.If stress is high enough to expand in the downstream adjacent channels section of shared public vertex, it will be according to certain ratio Bifurcated so that caused absolute stress is horizontal less than upper in by the fixed each adjacent TBC material volume of respective downstream groove segment limit The absolute stress swum in stress transfer TBC material is horizontal.Due to stress concentration sequentially more bifurcateds in cascaded fashion（Or It is bifurcated in the case of only having two downstream slot sections in three sections）, so that stress is diffused in turbine in a controlled manner The thermal barrier coating of part（TBC）Larger surface area on, this be finally decreased to may by local T BC layers absorb level.

More specifically, embodiments of the invention described herein are characterized by for exposure to burning gases The combustion turbine engine part of heat-insulated outer surface, such as, blade, stator blade, transition piece or ring segment wear parts.Part bag Include the metal substrate with substrate surface, and the anchor layer of structure on the substrate surface.Design surface feature（ESF）It is flat Face form pattern is formed in the anchor layer and protruded from the anchor layer.Thermal spraying or gas phase with TBC inner surfaces The individual layer or multilayer thermal barrier coating of the either solution/suspension plasma spray coating of deposition（TBC）Be applied to anchor layer it Go up and be attached to the anchor layer.TBC has the TBC outer surfaces for exposure to burning gases.Design cavity feature（EGF）It is flat Face form pattern is cut and formed in TBC outer surfaces and penetrated the TBC layer applied before.The EGF has groove depth. The plane configuration pattern on EGF style definitions overlyings summit, the overlying summit are correspondingly vertically-aligned with the corresponding ESF of lower section.EGF At least three corresponding groove sections in pattern are focused at each corresponding overlying apex in the form of more bifurcateds so that each assemble Groove section has the convergent channel section of at least two other adjoinings in each overlying apex.

Other embodiment described herein is characterised by having for exposure to the heat-insulated of burning gases for manufacturing The method of the combustion turbine engine part of outer surface, such as, blade, stator blade, transition piece or ring segment wearing terrain.Burning Turbine engine blade, stator blade, transition piece or ring segment wearing terrain are provided.The part being provided includes having substrate table The metal substrate in face.Anchor layer is formed on the substrate surface.Then, design surface feature（ESF）Plane configuration pattern shape Protruded into the anchor layer and from the anchor layer.The either vapour deposition or solution/suspension plasma of thermal spraying The individual layer or multilayer thermal barrier coating of body spraying（TBC）It is applied on the anchor layer.TBC have be applied to anchor layer it Go up and be attached to the TBC inner surfaces of the anchor layer and the TBC outer surfaces for exposure to burning gases.With groove depth Design cavity feature（EGF）Plane configuration pattern be cut and formed in TBC outer surfaces and penetrate the TBC applied before Layer.The plane configuration pattern on EGF style definitions overlyings summit, the overlying summit are correspondingly vertically-aligned with the corresponding ESF of lower section. At least three corresponding groove sections in EGF patterns are focused at each corresponding overlying apex in the form of more bifurcateds so that Mei Gehui Poly- groove section has the convergent channel section of at least two other adjoinings in each overlying apex.

Other embodiment of the invention described herein is characterised by the combustion turbine engine for control operation The thermal barrier coating of part（TBC）The method of Crack Extension in outer layer, such as, blade, stator blade, transition piece or ring segment abrasion Part.The part being provided includes the metal substrate with substrate surface.Anchor layer is formed on the substrate surface.Then, if Count surface characteristics（ESF）Plane configuration pattern formed in the anchor layer and from the anchor layer protrude.Thermal spraying or The individual layer or multilayer thermal barrier coating of the either solution/suspension plasma spray coating of vapour deposition（TBC）It is applied to substrate, The thermal barrier coating（TBC）With being applied on anchor layer and be attached to the TBC inner surfaces of the anchor layer and for sudden and violent It is exposed to the TBC outer surfaces of burning gases.Design cavity feature with groove depth（EGF）Plane configuration pattern be cut and formed Into TBC outer surfaces and penetrate the TBC layer applied before.The plane configuration pattern on EGF style definitions overlyings summit, the overlying Summit is correspondingly vertically-aligned with the corresponding ESF of lower section.At least three corresponding groove section meetings in the form of more bifurcateds in EGF patterns Gather in each corresponding overlying apex so that each convergent channel section has at least two other adjoinings in each overlying apex Convergent channel section.Engine including being provided part is operated, and the operation causes heat during engine thermal cycle in TBC layer Stress either mechanical stress or by foreign matter impact cause mechanical stress in TBC layer.What if any one was caused should Power is cracked in TBC, then when crackle intersects with one or more of EGF or ESF, Crack Extension is stopped in In TBC.

The individual features of each embodiment of the invention described herein can in any combination or sub-portfolio is entered The common application of row is applied respectively.

Brief description of the drawings

Consider in conjunction with the accompanying drawings it is following be described in detail it will be appreciated that the embodiment being illustrated and be described herein, in accompanying drawing In：

Fig. 1 is the one or more exemplary hot barrier coatings for including the present invention（“TBC”）The combustion gas of embodiment or combustion turbine hair The part axial cross-sectional view of motivation；

Fig. 2 is the detailed cross-sectional elevation view of Fig. 1 turbogenerator, and it illustrates the one or more examples for including the present invention The 1st row's turbine blade and the 1st row and the 2nd row's stator blade of property TBC embodiments；

Fig. 3 is turbine components（Such as, turbine blade, stator blade or combination section transition piece）Partial view, its With formation with reference to coating（“BC”）In design surface feature（“ESF”）Exemplary embodiment, wherein, TBC is coated in On ESF；

Fig. 4 is the partial view of turbine components, and it has the exemplary embodiment for the ESF being formed directly into substrate surface, Wherein, two layers of TBC is included coated in the bottom thermal barrier coating on ESF（“LTBC”）With coated in the outside thermal boundary on LTBC Coating（“OTBC”）；

Fig. 5 is the partial view of the exemplary embodiment of turbine components, and the turbine components have six on its substrate surface The entity protuberance ESF of side shape morphological configurations；

Fig. 6 is Fig. 5 ESF cross-sectional view；

Fig. 7 is the partial view for having the turbine components of multiple cylinders or columnar configurations ESF exemplary embodiment, and this is more Individual cylinder or columnar configurations ESF form hexagon plane form pattern, the hexagon in a joint manner on its substrate surface Plane configuration pattern surrounds or surrounded another column ESF being centered about；

Fig. 8 is Fig. 7 ESF cross-sectional view；

Fig. 9 is the combination coating with roughening（“RBC”）Exemplary embodiment turbine components partial view, this is thick The combination coating of roughening（“RBC”）On the ESF formed before in the BC of bottom, part is applied to before the BC of the bottom Substrate；

Figure 10 is the partial cross-section that the vertically and horizontally prior art turbine part that crackle is formed is undergone in double-deck TBC Figure, it is without figuratrix BC coated on similar no figuratrix substrate；

Figure 11 is the partial cross section view of the turbine components with the exemplary embodiment for forming the ESF in LTBC layers, its In, prevented by ESF and interrupted vertically and horizontally Crack Extension；

Figure 12 is the design cavity feature in TBC outer surfaces with formation（“EGF”）Exemplary embodiment turbine components Fragmentary, perspective view；

Figure 13 is the schematic cross section of the turbine components with the Figure 12 for forming the EGF in TBC；

Figure 14 is to be impacted by foreign matter so as to cause foreign object damage in TBC（“FOD”）The turbine components of Figure 13 afterwards Schematic cross section, wherein, prevent Crack Extension along the infall with EGF；

Figure 15 is the schematic cross section of the turbine components of Figure 13 after a TBC part is peeled off above crackle, It is lasting heat-insulated for being carried out to following turbine components substrate so as to leave intact TBC layer below crackle；

Figure 16 is the diagrammatic cross-sectional of the turbine components of the exemplary embodiment of the trapezoidal cross-section ESF with positive anchoring TBC Face figure, wherein, arrow points to the area of stress concentration in TBC；

Figure 17 is the schematic cross section of Figure 16 turbine components, wherein, angled EGF exemplary embodiment is Alignedly it is cut with area of stress concentration in TBC to alleviate potential stress concentration；

Figure 18 is the schematic cross section of the exemplary embodiment of the turbine components with both ESF and EGF；

Figure 19 is the schematic cross section of Figure 18 turbine components, wherein, FOD Crack Extensions have been subjected to ESF's and EGF Constraint；

Figure 20 is formed in the exemplary embodiment of the EGF in the turbine components TBC outer surfaces near part Cooling Holes, so as to Prevent the surface district on the opposite side of the extension of the crackle in the region around Cooling Holes or the layering arrival slot of TBC layer Domain；

Figure 21 is the schematic plan view of the exemplary embodiment of turbine components outer surface OTBC layers, wherein, the EGF of bifurcated exists Hexagon plane form pattern is wherein formed, the groove formed is assembled in the apex of hexagon, wherein, cause wherein OTBC ply stress in the OTBC materials along a upstream slot of Crack Extension is bifurcated at a pair of downstream slots, is thus prevented Other Crack Extension in OTBC materials；

Figure 22 is the alternate embodiment of turbine components outer surface OTBC layers, wherein, the EGF of bifurcated forms adjacent six sides wherein The plane configuration pattern of shape, wherein, the discontinuous groove formed is assembled in the apex of hexagon；

Figure 23 is the schematic plan view of the alternate embodiment of turbine components outer surface OTBC layers, wherein, the EGF of bifurcated is in portion The hexagon plane form pattern with different size and density is formed on part surface；

Figure 24 is the schematic plan view of the alternate embodiment of turbine components outer surface OTBC layers, wherein, the EGF of bifurcated is formed Adjacent outer hexagon, the outer hexagon and then the bifurcated EGF for surrounding the hexagon and triangular polygon that form nesting；

Figure 25 is the schematic plan view of the alternate embodiment of turbine components outer surface OTBC layers, wherein, the EGF of bifurcated is formed Outer hexagon, the convergent channel section summit of the outer hexagon are vertically aligned with the ESF protruded from substrate, the outer hexagon and then bag Enclose the bifurcated EGF to form the triangular polygon assembled at the central summit on central ESF；

Figure 26 is the schematic plan view of the alternate embodiment of turbine components outer surface OTBC layers, wherein, the EGF of bifurcated is formed Outer hexagon, convergent channel section summit and the ESF of the outer hexagon are vertically aligned, the outer hexagon and then encirclement formation adjacent six The bifurcated EGF of side shape and trapezoidal polygon；

Figure 27 is the schematic plan view of the alternate embodiment of turbine components outer surface OTBC layers, wherein, the EGF of bifurcated is formed Outer hexagon, convergent channel section summit and the ESF of the outer hexagon are vertically aligned, the outer hexagon so that surround formed have not With the adjoining hexagon and triangular polygon of size（Including the central nested hexagon being vertically aligned with central ESF）Point Pitch EGF；

Figure 28 is the schematic plan view of the alternate embodiment of turbine components outer surface OTBC layers, wherein, the EGF of bifurcated is formed Outer hexagon, convergent channel section summit and the ESF of the outer hexagon are vertically aligned, and the EGF formation of other bifurcateds is smaller The grid of hexagon.

In order to help to understand, make these accompanying drawings are denoted by the same reference numerals in the conceived case and shared Similar elements.Accompanying drawing is not drawn on scale.In any accompanying drawing, reference title " XX/YY " represent element " XX " or Any one in " YY ".In each inventive embodiments being described herein, rotated for size, fluid stream and turbine blade It is used for following common tokens：

D_GGroove depth；

The flow direction that F passes through turbogenerator；

G turbine blade tips are to wearing face gap；

H_RSpine's height；

R turbine blades direction of rotation；

R₁1st row's turbogenerator turbine；

R₂2nd row's turbogenerator turbine；

S_RSpine's centreline space away from；

S_GSeparation；

T thermal barrier coatings（“TBC”）Thickness degree；

The width of W surface characteristics；

W_GWell width；And

Stress concentration in σ TBC.

Embodiment

The exemplary embodiment of the present invention, which improves, is applied to turbine engine components（Including burning or gas turbine hair Motivation and steam turbine engines）Surface thermal barrier coating（“TBC”）Performance.The present invention being described in detail herein Exemplary embodiment in, in TBC（And more specifically, in TBC outer surface）Form design cavity feature（“EGF”）. In the case where multilayer TBC is applied, EGF is formed in outside thermal barrier coating（“OTBC”）Outer surface in, and optionally by Any desired depth is cut to, including is cut to substrate surface downwards.EGF width also optionally changes.EGF, which is formed, to be divided In the plane configuration pattern of fork, it means that multiple grooves are assembled, or from the point of view of another replacement relative perspective, and the plurality of groove is to pitch Shape pattern dissipates from public vertex.In three grooves in the embodiment that apex is assembled, it is arranged with bifurcated pattern, this Mean diverge to away from two of public vertex individually from any one groove close to public vertex（Therefore bifurcated 's）Path.In some embodiments being described herein, the EGF of bifurcated forms the plane configuration pattern of adjacent hexagon, the neighbour The adjoining hexagon for connecing hexagon and surrounding shares public groove and two summits.In certain embodiments, adjacent hexagon is outer Hexagon, it correspondingly surrounds other EGF plane configurations patterns（Such as, hexagon, trapezoidal and/or triangle）.In some realities Apply in example, bifurcated EGF plane configuration pattern summits and the design surface feature projected upwards from part substrate surfaces（“ESF”）It is perpendicular Directly it is aligned.

By making and the stress spread in the OTBC layers of a upstream slot adjoining to multiple downstreams by its public vertex Groove, the EGF of more bifurcateds make as caused by thermal-mechanical stress or by foreign object damage（“FOD”）Caused Crack Extension isolation is simultaneously And it is limited in TBC layer.In certain embodiments, the upstream thermal-mechanical stress applied is dissipated or declined by downstream public vertex groove Subtract.In other embodiments, the upstream thermal-mechanical stress applied it is sufficiently high so that with downstream bifurcated EGF adjoining TBC or There is fatigue crack in OTBC materials, until the stress is transferred to the bifurcated EGF of next group of convergence in plane configuration pattern.Quilt The stress of transfer and then bifurcated is carried out in cascaded fashion in next bifurcated EGF.When the stress concentration of bifurcated is fully decreased to In the downstream area of TBC or OTBC materials during complete attenuation, crackle is formed and is prevented from.In this way, with from part base In the case that the ESF that plate surface protrudes is vertically-aligned or not vertically-aligned, the EGF patterns of bifurcated cause outside TBC or OTBC Surface self can be absorbed in the surface area of minimum and the caused thermal-mechanical stress that dissipates.Therefore, TBC is also caused Or Crack Extension and/or caused peeling minimum on OTBC outer surfaces.

The TBC of thermal spraying summation

Application in combustion turbine engine part

Referring to figs. 1 to Fig. 2, turbogenerator（Such as, combustion gas or combustion turbine engine 80）Including compound compressor section 82, burning block 84, multistage turbine section 86 and gas extraction system 88.Generally in the axial length along turbogenerator 80 On flow arrow F direction, the air inlet of atmospheric pressure is sucked in compressor section 82.Air inlet is more in compressor section 82 Row's rotatable compressor blades are progressively pressurizeed, and the compressor stator blade to be matched is guided to burning block 84, herein, air inlet with Fuel is mixed and lighted a fire.The ignited fuel/air mixture being now arranged in compared with original air inlet under bigger pressure and speed is mixed Compound is conducted through the successive vanes that transition piece 85 is reached in turbine 86 and arranges R₁、R₂Deng.The rotor and axle 90 of engine have There is multiple rows of airfoil cross-section shape turbine blade 92, the turbine blade 92 is terminated in compressor section 82 and turbine 86 Distal end vane tip 94.

For the sake of for convenience and simplicity, to the thermal barrier coating on engine components（“TBC”）It is discussed further by emphasis Be placed on turbine 86 embodiment and application it is upper, but similar constructions be applicable to compressor section 82 or burning block 84 with And steam turbine engines part.In the turbine 86 of engine 80, each turbine blade 92 has spill configuration high Press side 96 and convex low-pressure side 98.The Cooling Holes 99 formed in blade 92 contribute to cooling fluid to pass through along blade surface. The high speed and high pressure burning gases flowed on the F of combustion flows direction apply rotary motion on blade 92, so that 90 turns of rotor It is dynamic.It is well known that some mechanical outputs being applied on armature spindle 90 can be used for performing useful work.Burning gases are in rotor 90 Distal end is constrained by turbine casing 100 and constrained in the near-end of rotor 90 by the gas seal member 102 including wearing face.

The 1st row's section shown in reference picture 2, corresponding upstream vane 104 and downstream vane 106 are distinguished substantially parallel Upstream combustion gas is guided in the incidence angle of the leading edge of turbine blade 92, and reboots the trailing edge for leaving blade 92 Fired downstream gas enters the row's turbine blade of downstream the 2nd with desired entering angle（It is not shown）.Formed in stator blade 104 and 106 In Cooling Holes 105 contribute to cooling fluid along stator blade surface pass through.It should be noted that the He of Cooling Holes 99 shown in Fig. 2 105 only schematically show, in order to which vision understands and is exaggerated, and are not drawn on drawing.Typical turbine blade 92 Or stator blade 104 and 106 has more Cooling Holes around the distribution of corresponding aerofoil profile body, relative to exposed to engine combustion The respective vanes or stator blade total surface area of gas, the Cooling Holes have much smaller diameter.

As it was previously stated, it is generally configured with being used to make substrate insulation below exposed to the turbine components surface of burning gases TBC layer.Typical TBC coating surfaces include turbine blade 92, stator blade 104 and 106, ring segment 120 and related whirlpool Turbine stator blade holder surface and burning block transition piece 85.For blade 92, stator blade 104 and 106, ring segment 120 and transition The TBC layer of the exposed surface of part 85 generally by thermal spraying or vapour deposition or solution/suspension plasma spray process come Coating, wherein, total TBC layer thickness is 300-2000 microns（μm）.

Turbine blade tip wear parts TBC is applied

Thickness is more than 1000 microns（μm）Insulating barrier be generally applied to the wear-resisting ring segment part of fan-shaped turbine blade tip 110（Hereinafter, also collectively referred to as " wear parts "）, the part makes the turbine casing 100 of turbogenerator 80 opposite with vane tip 94 Ground is linear.Wear parts 110 have the support surface 112 for being maintained in shell 100 and being attached to shell 100 and insulation Wear-resisting substrate 120, the wear-resisting substrate 120 that insulate have in a confronting relationship with vane tip 94 and separate blade tip clearance G's Outer surface.Wearing face 120 is generally by with being applied to blade 92, stator blade 104 and 106 and the burning gases exposure table of transition piece 85 The metal/ceramic material construction that the TBC coating materials in face are similar forms.These wearing face materials have high heat resistance and resistance to Heat erosion, and structural intergrity is maintained at high combustion temperatures.Generally, it should be understood that some form of TBC layer is formed For insulation protection on the exposed lower-lying metal support surface substrate 112 of vane tip wear parts 110, plus The dielectric substrate thickness protruded at additional height on TBC.It is to be understood, therefore, that ring segment wear parts 110 have work( Can on be equal to the TBC layer of the TBC layer applied on turbine transition piece 85, blade 92 and/or stator blade 104/106.It is wear-resisting Surface 120 is functionally similar to protect extra play of the wear parts support surface substrate 112 from wearing and providing Thermal protection Sole or heel of a shoe.Exemplary materials for vane tip wearing face spine/groove include pyrochlore （pyrochlore）, cubical or partially stabilized yittrium oxide, and stable zirconium oxide.Because wearing face metal is made pottery Ceramic material is generally more easy to wear than the material of turbine blade tip 94, so maintaining blade tip clearance G to avoid two phases To the contact between part, the contact may cause too early vane tip to be worn and the worst at its best In the case of may cause engine damage.

Ring segment wear parts 110 are generally configured with metal base support surface 112, thousands of micron thickness（I.e., typically Several times of the TBC layer thickness of transition piece 85, blade 92 or stator blade 104/106）Thermal spraying the wear-resisting substrate layer of ceramic/metal It is applied to the metal-based layer support surface 112.As being more fully described herein, the correlation claimed priority herein is specially The form of 120 wearing face of ring segment 120 and protuberance configuration embodiment described in profit application are included in wear-resisting substrate layer 120 Groove, depression or spine are to reduce wearing face material cross-section, for reducing the abrasion of potential vane tip 94 simultaneously And for guiding combustion-gas flow in gap area G.Improve engine efficiency and drive production to save the commercial requirements of fuel Smaller blade tip clearance G specifications are given birth to：Preferably not more than 2 millimeters and desirably close to 1 millimeter（1000 μm）.

Design surface feature（“ESF”）Improve TBC adhesion strengths and crackle isolation

Some exemplary turbine unit embodiments include ESF anchor layer, and it contributes to the mechanical interlocked of TBC layer and helped In isolating the crackle in TBC layer, so that crackle is not diffused into outside ESF.In some vane tip wear resistance applications, depend on The physical size of surface characteristics and the relative spacing between it are protruded in entity spine and groove, entity spine and groove protrude surface Feature and micro- surface characteristics（“MSF”）As ESF, but it is for more generally applying in addition to vane tip wear parts Turbine components for it is too big.For exemplary turbine blade, stator blade or combustor transition piece application, ESF is formed Be attached in the anchor layer of the interior surface layers of TBC layer, and do not change exposed to burning gases TBC layer otherwise In the case of the outer surface of flat, the anchoring that is sized to of the ESF is applied to the thickness ranges of these parts and is 300-2000 microns（μm）TBC layer coating.Generally, ESF has the gross thickness being enough in TBC layer on turbine components surface The interior height and three-dimensional configuration spacing that mechanical anchor and crackle isolation are provided.Therefore, ESF will be more shorter than total TBC layer thickness, but compare Etching or engraving surface characteristics it is higher, the etching or engraving surface characteristics it is said that be provided to improve TBC with Adjacent lower floor（For example, the exposed substrate in lower section or the middle BC layers being placed between exposed substrate and TBC layer）Between bonding With reference to.Generally, in the exemplary embodiment, ESF has 75 about 2 the percent to percent of the gross thickness of TBC layer （2-75%）Between projecting height.In some preferred embodiments, ESF has at least about the percent of the gross thickness of TBC layer 33（33%）Projecting height.In some exemplary embodiments, ESF is limited bigger by least hundred than equivalent flat surfaces product / bis- ten（20%）Total surface area.

Fig. 3 and Fig. 4 shows the exemplary embodiment for the ESF to be formed in the anchor layer of inner surface of TBC layer is attached to. TBC layer 306/326 can include multilayer TBC material, but finally will at least have the appearance included for exposure to burning gases The TBC in face.In figure 3, turbine components 300/320（For example, combustor section transition piece, turbine blade or turbine Stator blade）With the metal substrate 301 protected by overlying TBC.BC layers 302 are fabricated and coated in other undistinguishable substrates On 301, this includes ESF 304 plane configuration pattern without feature substrate 301.These ESF 304 direct shapes in the following way Into in BC：（i）The known thermal spraying of molten particles to establish surface characteristics, or（ii）The known increasing material layer of surface characteristics Manufacture establish application, such as, by 3D printing, sintering, electronics either laser beam deposition or（iii）Known baseplate material Ablation remove processing technology, so as to by the part not removed limit feature.ESF 304 and BC layers 302 exposed surface Remainder can receive other surface treatments, for example, surface roughening, microscopic carvings quarter or light etching process, to improve The adhesion strength of the TBC layer 306 of subsequent thermal spraying.Therefore, the remaining exposed surface of ESF 304 and BC layers 302 includes being used for TBC layer 306 anchor layer.The outer surface of TBC layer 306 is exposed to burning gases.

In Fig. 4, turbine components 320 construct with anchor layer, wherein, ESF 324 form array passes through known Directly casting is formed directly into other no feature substrate 321, either by thermal spraying, increase material layer and establish or alternately Removed by the ablation of known baseplate material or other machinery, processing technology is established on the surface of the substrate, baseplate material Ablation or other machinery remove, processing technology feature is limited by the remainder for the substrate not removed.The Hes of ESF 324 The exposed surface of exposed substrate 321 can receive other surface treatment, for example, surface roughening, microscopic carvings are carved or photoetch Technique, to improve the adhesion strength of the TBC layer 326 of subsequent thermal spraying.Therefore, in the case of no any middle BC layers, ESF 324 and exposed substrate surface include for TBC layer 326 anchor layer.Multilayer TBC layers 326 are applied on anchor layer. The multilayer TBC layer 326 includes the bottom thermal barrier coating for being attached to anchor layer（“LTBC”）327 layers,（In certain embodiments, LTBC is used as a part for anchor layer）And the outside thermal barrier coating with the outer surface for exposure to burning gases （“OTBC”）Layer 328.Additional TBC intermediate layers 326 can be applied between LTBC layers 327 and OTBC layers 328.In some implementations In example, multilayer TBC layer is applied on any other type of ESF having been described above before.For example, although not in the drawings Show, but the modified example of the construction of Fig. 3 turbine components 300（Wherein, ESF 304 is formed in BC layers 302）With similar The multilayer TBC 306 of TBC layer 326 on coated in ESF 304.

During the design and manufacture of turbine components, thus it is possible to vary ESF cross sectional configurations, its form array pattern and Its corresponding size suppresses crackle formation, Crack Extension and TBC layer peeling to optimize Thermal protection will pass through.Show in Fig. 5 into Fig. 9 The different exemplary arrangements of ESF cross sectional configurations, its three-dimensional configuration array pattern and its corresponding size are gone out.In these accompanying drawings In, it is illustrated that the well width between ESF height, ESF spines width, spine's spacing and spine.In the exemplary of Fig. 5 to Fig. 9 In embodiment, ESF is selectively arranged in three-dimensional configuration linearly or in polygon pattern.For example, shown in Fig. 7 and Fig. 8 The ESF plane configurations pattern of parallel vertical protrusion also can in the accompanying drawings with orthogonally or be in plane prominent outside accompanying drawing Repeat to angle of inclination.In fig. 5 and fig., turbine components 340 have metal substrate 341, wherein, shape in metal substrate 341 Into there is ESF 344, include the hexagonal configuration of the double flute of the upper groove of encirclement.In figures 7 and 8, turbine components 350 have metal Substrate 351, wherein, formed with ESF 354, including cylindrical pin in metal substrate 351.In order to which Fig. 5 to Fig. 8 vision is succinct Property, turbine components 340 and 350 are shown as the TBC layer without covering ESF 344 or 354.ESF 344 or 354 is logical Repeated at least a portion on the surface of the corresponding substrates of Chang Qi.The spacing pitch and footprint size of three-dimensional planar form pattern Also can partly be changed on the surface topology of turbine components.

Although the ESF that Fig. 5 is shown into Fig. 8 is formed directly on its corresponding substrate, as it was earlier mentioned, it can be formed Coated in without in the BC on feature substrate.It is also noted that can be by applying coarse knot on anchoring layer surface Close coating（“RBC”）Layer realizes additional anchor ability, such as, the RBC layers 365 of the turbine components 360 shown in Fig. 9.Though Right RBC 365 is shown as being coated on BC 362 and its ESF 364, but the RBC 365 or other types of BC 362 Also can be applied directly on parts metals substrate 361.

As mentioned previously, in addition to the TBC layer anchoring advantage that ESF described herein is provided, it is further defined TBC layer Crack Extension.In Figure 10 turbine components 380, formed in double-deck TBC386 outer TBC layer 388 thermally-induced And/or crackle 389V and 389H caused by foreign matter.Generally there is the interior TBC layer 387 of the material character different from outer TBC layer 388 It is attached to BC layers 382, and BC layers 382 and then is attached to parts metals substrate 381.The vertical crackle 389V' of the rightmost side has worn long Thoroughly to the interface of outer TBC layer 388 and interior TBC layer 387, and now just with crackle 389H horizontal extensions.Crackle 389H's enters The extension of one step may cause outer TBC layer 388 to be layered from the remainder of turbine components 380, and finally cause positioned at last The potential peeling of all outer material of TBC layer 388 between the vertical crackle 389V' in side and the vertical crackle 389V in the leftmost side.Peel off most The overall thermal insulation protection to the lower-lying metal substrate 381 below spall can be reduced eventually.

The resistance to crack extension construction of the turbine components 390 relatively shown now in Figure 11.Metal substrate 391 is in layer 382 On also there is BC, TBC layer 396 is attached to the BC.TBC layer 396 further comprises bottom thermal barrier coating（“LTBC”）397, should LTBC 397 have ESF 394 formed therein for outside thermal barrier coating（“OTBC”）398 interlockings.Therefore, have Its ESF 394 LTBC layers 397 effectively serve as the anchor layer of OTBC layers 398.In certain embodiments, LTBC layers 397 have The intensity and ductile material property higher than OTBC layer 398, and OTBC layers 398 have higher thermal resistance and fragile material Matter.Vertical crackle 399V has extended through OTBC 398 whole thickness, but is had blocked in LTBC 397 interface Other vertical extension.Although vertical crackle 399V has been spread to form horizontal crackle 399H along OTBC/LTBC interfaces, Horizontal crackle extension is further prevented from when the vertical wall with the ESF 394 positioned at horizontal crackle area side intersects so that OTBC 398 potential layering is limited to the well width between ESF 394.If whole or portion above horizontal crackle 399H OTBC layers 398 are divided to be peeled off from the other parts of part, then now exposed LTBC 397 relatively small surface area will be more preferable Resist the potential fire damage to lower section turbine components substrate 391 in ground.Similarly, on the top of the ESF 394 with the adjacent crackle When portion's ridge surface intersects, vertical crackle 399V' vertical extension is prevented from.Prevent crackle 399V' other vertical extension Reduce the possibility that the OTBC 398 around crackle is peeled off.

Design cavity feature（“EGF”）Improve the isolation of TBC crackles

Some exemplary turbine unit embodiments include the design cavity feature of form array（“EGF”）, the form array sets Cavity feature is counted to be formed in the outer surface in TBC after TBC layer coating.Groove depth and width optionally change.In some realities Apply in example, groove is cut some or all thermal barrier coatings, design surface feature（ESF）, with reference to coating（BC）In, or very To cutting in lower substrate surface.It is in arbitrary inclination that EGF fluted shafts line, which is optionally oriented relative to TBC outer surfaces, And extend in TBC layer.Similar to fire fighter's fire line, EGF isolates the crackle in TBC layer so that crackle will not be across More the border extension in groove space is into the other parts of adjacent TBC material.Generally, if the crackle in TBC ultimately results in crackle The peeling of the material of top, then the localization boundary perimeter of position is peeled off in the EGF arrays formation around the crackle, so that border Outer TBC material remains intact.In the spall defined by EGF, it will usually be limited to lose above EGF groove depths by damage Material.Therefore, in many exemplary embodiments, EGF depth is limited to less than to the gross thickness of whole TBC layers so that still The intact TBC material of certain volume and depth so be present to provide Thermal protection for local lower part metal substrate.One In a little embodiments, EGF arrays are combined with ESF arrays may be single to provide any one of the EGF arrays and ESF arrays Additional TBC integralities outside the integrality solely provided.

Figure 12 and Figure 13 shows the turbine components 400 with lower-lying metal substrate 401, and TBC substrates 402 are attached to this On lower-lying metal substrate 401, TBC substrates 402 are orthogonal with the exemplary three dimensional form array formed afterwards in TBC layer coating The design cavity feature EGF 403 and 404 that ground intersects.Groove 403 and 404 is configured with one or more groove depth D_G, well width W_G, groove Interval S_GAnd/or polygon form array pattern.With any different groove depths, spacing, width and polygon plane form Multiple cavity features of pattern can partly change around the surface of turbine components 400.For example, three-dimensional configuration polygon pattern It can be repeated on all or part of parts surface, and groove depth can change on the surface.Although TBC layer 402 It is shown as being attached directly to substrate 401, but in other exemplary embodiments of the invention, the intermediate anchor layer structure described before can be used Make to replace, including one or more combines coating（“BC”）Or bottom thermal barrier coating（“LTBC”）.

Exemplary design cavity feature is shown in Figure 14 and Figure 15（“EGF”）Crackle isolating power, wherein, turbine components 400（Such as, burning block transition piece 85, turbine blade 92 or turbine vane 104/106）By foreign matter（“FOD”）Punching Damage is hit, so as to cause vertical the crackle 408V and horizontal crackle 408H in the outer surfaces 405 of its TBC 402.Damaged positioned at impact The EGF 404 of traumatic part side prevents the other Crack Extension across groove space, so that the TBC material of trough rim out-of-bounds is from another Outer cascade Crack Extension.If the TBC material in impact zone peels off from TBC outer surfaces 405, by crackle and hole shape bottom surface The intact and unmarred material protection lower-lying metal substrate 401 of " hollow " TBC layer 402 of 406 remaining defined is not by other damage Wound.

With creating the existing known of space or discontinuous portion in the thermal spraying being coated or the TBC layer of vapour deposition TBC stress cracking relieving mechanisms（Such as, by changing layer coating orientation or material porosity）Difference, design groove herein Feature（“EGF”）Embodiment forms cutting or ablation the groove that desired depth is reached by the TBC layer outer surface formed before Or other spaces.As shown in Figure 16 and Figure 17, turbine components 410 have anchor layer 412, and anchor layer 412 includes trapezoidal horizontal stroke Cross-sectional configuration design surface feature（“ESF”）414.Arrow in Figure 16 shows to be located at ESF during turbine engine operation 414 overlapping edges or the reality of apex or potential thermal stress or mechanical stress concentration area σ in TBC layer 416 can Can place.Correspondingly, EGF 418 is cut to by TBC outer surfaces with an angle along line of tension σ at tipper axis angle In.EGF 418, which is also cut, to be cut up to sufficient depth to intersect with the summits of ESF 414.In EGF 418 any in TBC layer 416 Caused stress will not extend to opposite side from side on side.TBC layer 416 on EGF 418 either side can be empty along groove Gap is freely expanded or shunk, so as to further reduce the possibility for producing the crackle parallel to groove.

Figure 17 to Figure 19 turbine components are implemented to be illustrated by design cavity feature（“EGF”）With design surface feature （“ESF”）Combination provide additional TBC crackles suppress and isolation advantages.In figure 16, by being formed all the way through TBC 416 Depth until its with EGF 418 that the ESF 414 of anchor layer intersects realize release it is actual or potential line of tension σ it is excellent Point.In Figure 18 and Figure 19 embodiment, turbine components 420（For example, turbine blade either stator blade or transition piece）Gold Category substrate 421, which has, combines coating（“BC”）422 anchor layers, the anchor layer, which defines, to be oriented in three-dimensional planar form pattern Design surface feature（“ESF”）424.TBC layer 426 is applied on anchor layer, and afterwards, EGF 428 another shape State three-dimensional pattern is cut through exposed to the TBC layer outer surface 427 of burning gases.The plane configuration patterns of EGF 428 can not It is same as the plane configuration patterns of ESF 424.If using identical plane configuration pattern to ESF and EGF, its corresponding pattern need not （It is multiple）It is vertically-aligned in TBC layer.In other words, EGF and ESF can be in the surely single three-dimensional of the part upper limit, independent alignment Plane configuration pattern.In certain embodiments, ESF and EGF has the three-dimensional planar form pattern repeated respectively.Each pattern can Partly to change around parts surface.

In figure 18, the plane configuration patterns of EGF 428 with the patterns of ESF 424 repeat corresponding to any specific side of alignment Formula.Some in EGF 428 are cut in the spine's platforms of ESF 424, and other EGF 428 are only cut TBC 426 In layer.In Figure 19, foreign matter（“FO”）TBC outer surfaces 427 have been impacted, have been created that by ESF 424A and 424B and EGF The crackle that 428A and 428B is prevented, ESF 424A and 424B and EGF 428A and 428B define or otherwise surrounded FO Impact zone.If the TBC material 426B above crackle separates with the remainder of the TBC layer of turbine components 420, in " hole It is hollow " base portion at be still attached to remaining of BC anchor layers 422 and do not damage TBC material 426A metal substrate 421 below is carried Heat supply is protected.

Design cavity feature（EGF）

Suppress the TBC layerings around Cooling Holes

Advantageously, cavity feature is designed（“EGF”）It can be formed in discontinuous around turbine components Cooling Holes or other surfaces In the TBC layer of some or all of circumference in portion, to be limited in along the Cooling Holes in part substrate or other discontinuous The layering of TBC on the layer at edge.TBC layer at the extreme edge of Cooling Holes can initiate the separation with metal substrate, The separation can away from the hole in TBC layer laterally/flatly spread.Laterally spaced apart with Cooling Holes edge Place（Such as, in the depth contacted with anchor layer or metal substrate）EGF formation can limit other point beyond groove Layer.

In fig. 20, turbine components 490（For example, turbine blade or turbine vane）With multiple corresponding coolings Hole 99/105, the plurality of corresponding Cooling Holes 99/105 are surrounded completely by the linear EGF sections 494 and 496 of turbine components 490, whirlpool The linear EGF sections 494 and 496 of turbine component 490 make Cooling Holes 99/105 from fully or partly being surrounded each other.Along The TBC layerings of one or more circumferential edges of Cooling Holes 99/105 are prevented from the intersection of peripheral EGF sections 494 and 496.In order to For purpose of brevity, further describing for device to hole circumference EGF is limited to groove shape and orientation.Lower substrate, anchor layer, ESF and it is any its Its EGF existing descriptions of description before are constructed.

Design cavity feature（EGF）Pattern arrays

The Crack Extension of bifurcated or prevention in a manner of concatenated in order

Figure 21 to Figure 28 design cavity feature（“EGF”）Plane configuration pattern embodiment includes convergent channel section, and at least three assemble Groove section shares public vertex in a repetitive fashion.In the geometric aspects of correlation, each groove end is punished in its public vertex and pitched Or at least two other diverging grooves are branched into, it is similarly to upper water stream and is divided into two downstreams tributary.In bifurcated current, Flow is divided between the tributary of two downstreams.Downstream flow in any tributary is both less than upstream flowrate.Similarly, bifurcated EGF embodiments in multiple downstream slot local materials bifurcated either divide along upstream formed groove be applied to TBC or The upstream stress of OTBC local materials.Local downstream material in TBC or OTBC absorbs being drawn by public vertex border Rise（Present bifurcated）Or the application stress reduced.If there is downstream local material enough intensity to avoid brokenly Split, then thus prevent any upstream to rupture.If downstream local material ruptures, the stress being applied in（And possible split Line）Ensuing one or more public vertex are extended in cascaded fashion.Cascade extension continues until stress reduces To being enough to prevent other crackle from being formed.

Figure 21 is the design cavity feature of the bifurcated in the TBC outer surfaces of turbine blade, stator blade or transition member 500 （“EGF”）Exemplary embodiment view.EGF forms the hexagon shape or honeycombed planar shaped of adjacent hexagon 502 Aspect formula, it correspondingly has six grooves 504, and six grooves 504 are terminated at six summits 505.The hexagon 502 of each pair adjoining Share public groove section 504A and a pair two summits 505A and 505B.Each shared public vertex 505 has three convergent channels Section 504.In symmetrical hexagon, three grooves 504 at each shared summit 505 are with 120 degree of orientations.Then each shared Summit（For example, see summit 510）Place, three convergent channels（For example, see groove 509,511 and 512）Correspondingly bifurcated is other two Individual adjacent channels（For example, see that the bifurcated of groove 509 is groove 511 and 512）.In other words, if a groove is along one in convergent channel Path towards summit advance, then then can bifurcated be two downstream slots.

Figure 21 bifurcated（Or in certain embodiments it is more bifurcateds）Groove geometry concept for prevent OTBC Or the Crack Extension in TBC outer surfaces is useful, no matter the stress for causing crackle in TBC is drawn by thermal-mechanical stress Rise, or caused by heating transient state, or by foreign object damage（“FOD”）Impulse machine stress causes.Reference picture 21, originates in The stress σ for causing crackle in the border of hexagon 506 and 507_AIt will be dissipated by the TBC material volume in these hexagons（That is, It is prevented from wherein）, or crackle caused by stress in TBC material is most at last in the peripheral hexagonal boundaries of hexagon 508 In intersect with one or more groove sections 511 and 512.If stress σ_AIn any groove（Such as, groove 509）Interior extension, then it will：（i）All it is prevented from before border vertices 510 are reached, or（ii）The extension stress σ of continuation_BAnd σ_CInto shared public top In two adjacent downstream slot sections 511 and 512 of point 510.As stress σ_AExtend to two adjacent downstream slot sections 511 and 512 When middle, the stress carries out bifurcated with certain ratio so that in each adjacent six defined by respective downstream groove section 511 and 512 Side shape（It is hexagon 508 herein）In the caused horizontal σ of absolute stress_BAnd σ_CShifted less than upstream in hexagon 506 and 507 The horizontal σ of absolute stress_A.When stress concentration sequentially bifurcated in cascaded fashion（Or in more than two downstream slot section It is more bifurcateds in situation）When, so that stress is in a controlled manner in the outside thermal barrier coating of turbine components（“OTBC”）Compared with Spread on high surface area, this is finally decreased to the level that can be absorbed by local T BC layers.If EGF any one or it is more Local stress in individual honeycomb, hexagon plane form pattern 502 is enough to crack, then the adjoining at cascade summit 505 Honeycomb EGF sections will make stress bifurcated, until Crack Extension is prevented from.At each summit 505, exist stress local diffusion to its Its downstream slot section, or local prevention/decrease of the stress in self-forming pattern.

As shown in the hexagon plane form pattern embodiment 522 in Figure 22, hexagon plane form pattern is formed EGF grooves section 524 is discontinuous, and the groove connected jointly is not converged at each summit 525, this and six in Figure 21 The continuous connectivity slot 504 of side shape plane configuration pattern 502 is different.Cutting is formed in the groove of some laser ablations or water spray cutting In technique, it is easier to form discontinuous groove.When stress caused by crackle reaches discontinuous groove（Such as, groove 524A）End When, crackle is by across the entity TBC material at Local Vertex 525A and self extension and bifurcated to adjacent downstream slot In 524B and 524C.In other words, under thermal-mechanical stress, crack growth will be effectively combined into discontinuous groove section jointly to connect Logical section, as being just formed by as its script.The discontinuous EGF grooves section construction shown in Figure 22 can be incorporated into knot Close in any EGF embodiments for showing and describing in any other accompanying drawing herein, include Figure 21 and Figure 23 to Figure 28 reality Apply example.

In fig 23, adjacent hexagonal honeycomb pattern in blade, stator blade, ring segment or the TBC of transition member 540 or There is different size and pitch density in the different surfaces region of person's OTBC coating outer surfaces.For proposed structure most Good length dimension will depend on TBC system（That is, basic material, with reference to coating and TBC layer）, during engine operating cycle Local temperature differential and part local shape face.Therefore, in the different zones on the surface of part, local pitch and density sample Formula is expected operating condition for it and optimized.For example, compared with the distance in the leading edge of blade, on hexagon summit and its The distance between convergent channel section may be in the root of blade or bucket platform of turbine blade（platform）It is bigger in part. EGF pitches and density are according to shape face difference, local thermal stress and foreign object damage（“FOD”）Risk partly customized. Emphasis sees blade inlet edge operating condition, its relatively large curvature, it is highly exposed carried secretly in burning gases and burning gases it is different Thing, and TBC burning pollutant propensity for degradation in higher density, less honeycomb pattern, such as, the rightmost side in Figure 23 Plane configuration pattern 542 those density and honeycomb pattern, but blade pressure side surface then may tend in the figure The honeycomb pattern 544 of middle size in middle body.Relatively large honeycomb pattern 546 on Figure 23 leftmost side may fit Side surface and bucket platform are sucked together in blade.

EGF grooves cross-sectional depth and width can be in blade, stator blades either outside TBC the or OTBC coatings of transition portion 550 Optionally localized variation in the different surfaces region on surface, so as to proof stress and Crack Extension, as shown in Figure 24.Outside Enclosing in hexagon includes polygon plane form pattern, for further controlling local Crack Extension.Here, in continuous level Outer hexagon 560 in form pattern surrounds two nested hexagons：Middle hexagon 570 and interior hexagon 580.Corresponding embedding Area filling between set hexagon 560,570,580 has the triangle subarea 590,600,610 of shape triangular in shape, its In, each triangular apex has at least three convergent channel sections.Triangle 590 includes groove section 592 and public vertex 594.With it is outer The each several part of groove section 592 and groove section 562 that hexagon 560 abuts is coextensive, and in some positions, the He of public vertex 564 594 is coextensive.Similarly, it is coextensive with each several part of the groove section 592 and groove section 572 of the adjoining of middle hexagon 570, and In some positions, public vertex 574 and 594 coextensive.Moved inward in the hexagon pattern of nesting, triangle 600 has There are three groove sections 602 and public vertex 604.In some positions, groove section 602 is prolonged jointly with adjacent groove section 572 or 582 Stretch, it forms hexagon 570 and interior hexagon 580 among corresponding, and public vertex 604 in some positions with public top Point 574 or 584 is coextensive.Using nested hexagon and triangle bifurcated the groove pattern of TBC or OTBC outer surfaces 550, So that the stress concentration of crackle is formed by by the stress distribution of the range constraint of exemplary triangles 610 to one or more summits 614 or 584.Those summits have a groove section of corresponding downstream bifurcated, the groove section formed other adjoining triangles 610 or Interior hexagon 580.Cause the stress of crackle as its cascade passes through the downstream of groove section 612 or 582 each cascade, continuous OTBC materials and dissipate.If the crackle in any one or more triangles 610 or hexagon 580 is enough to cause part Surface is peeled off, then passes through remaining unmarred adjacent polygon（Such as, triangle 600）Minimize exfoliation surface damage It is and restrained.

Generally, forming cascade EGF each groove has the groove size or plane configuration pattern of any desired, such as herein Describe before.As shown in Figure 24, outer hexagon 560 has than inner peripheral polygon 570,580,590,600 or 610 more Wide and/or deeper groove 562.In fig. 24, middle hexagon groove 572 is more narrower than groove 562 and/or more shallow, and groove 582 and then ratio Groove 572 is narrower and/or more shallow.In certain embodiments, in adjacent triangle relative to nested hexagon groove 562,572 and/ Or 582 any one in middle and inclined groove 592,602 and/or 612 is more shallow than those grooves of aforementioned hexagonal shape groove It is and/or narrower.Any foregoing bifurcated groove is all formed by manufacture method previously described herein.Assembled in each apex More multiple-grooved section makes the quantity of upstream stress and those sections proportionally bifurcated.In this way, the more bifurcateds in any downstream are transferred to The stress of the fixed OTBC materials of groove segment limit is less than the stress being transferred in the OTBC materials defined in the transfer groove section of upstream.

Compound vertically-aligned design surface feature（ESF）

And design cavity feature（EGF）

In certain embodiments（Such as, in fig. 25）, there is thermal barrier coating（“TBC”）Blade, stator blade, ring segment abrasion-proof gauge Face or burning gases transition member 630 have compound vertically-aligned design surface feature（“ESF”）632 and 634 and Design cavity feature（“EGF”）642 and 652, it controls ESF enhanced propertied " fire wall " and " hollow " with EGF of coating anchoring Scaling property processed is combined.Before as shown in Figure 19, ESF 424A and the 424B enhancing for defining " hollow " of peeling are surplus Anchorings of the remaining OTBC materials 426A in " hollow ".Figure 25 is back to, ESF 632 and 634 is with the density of any desired, cross section Area or height are constructed, as described above.In Figure 25 embodiment, the ESF 632 of multiple cylinder forms（Have Circular cross section）It is aligned with the summit 644 of the EGF grooves section 642 of hexagon plane form pattern outside overlying 640.ESF 632 has The construction similar to Fig. 7 and Fig. 8 ESF 354.Alternatively, ESF is formed in hexagon sample as Fig. 5 as Fig. 6 ESF 344 In formula.

In Figure 26 to Figure 28 embodiment, corresponding turbine vane, blade, ring segment wearing face or combustion gas Body transition member has the plane configuration pattern of adjacent corresponding outer hexagon 670 or 690 or 710, and these outer six The respective vertices 674 or 694 or 714 of side shape are in corresponding cylindrical EGF 676 or 696 or 716 areas Oriented in form perpendicular alignmnet.Also have in each corresponding ESF plane configuration patterns central ESF 678,698 or 718.In Figure 26 into Figure 28, the pattern of less polygon hexagon 680,700 or 702 or 720；Semi-hexagon shape shape Trapezoidal the 682 of shape, or trapezoidal the 705 of 1/3rd hexagonal shapes；Or triangle 704 by corresponding outer hexagon 670, Or 690 or 710 surround.The peeling of any less polygon leave covering and guard block it is remaining smaller polygon Shape.In figure 27, desired higher density, it is less individually surface area polygon in the case of, smaller polygon be by The peripheral hexagon 700 of larger outer hexagon 690,702, triangle 704 and trapezoidal 705 combination.In certain embodiments, scheme 25 to Figure 28 outer hexagon 640,670,690 and/or 710 in larger periphery abuts with other similarly sized hexagons, or It is abutted with smaller hexagon, such as in Figure 23 form local pattern.Alternatively, Figure 25 to Figure 28 plane configuration pattern is The outer hexagon that is arranged according to uniform either different pitch and size pattern or individually independent outer hexagon 640th, 670,690 and/or 710 discontinuous cluster.

More specifically, Figure 25 to Figure 28 bifurcated groove EGF patterns are further limited in adjoining in each outer hexagon The plane configuration pattern of polygon.Adjacent inner polygon shares at least one public inner polygon summit respectively, and each Inner polygon is completely enclosed in corresponding corresponding outer hexagon 670,690 or 710 respectively.Moreover, in EGF patterns extremely Few three corresponding bifurcated groove sections are focused at each corresponding outer hexagon or inner polygon apex in a manner of bifurcated pattern, So that each convergent channel section has the convergent channel section of at least two other adjoinings.A large amount of convergent channels in plane configuration pattern can increase Add the bifurcated of stress transfer.By the way that ESF and EGF are combined, it is more likely that peeling off the hole that will be left behind " hollow ", and remain Remaining TBC material then protects lower substrate surface, no matter the peeling of outermost material surface, such as Figure 19.Implemented by Figure 25 to Figure 28 The more high density pattern for the polygon that the hexagon of example surrounds is suitable for the leading edge of turbine blade and stator blade.

In certain embodiments, the larger hexagon EGF with or without the vertically-aligned ESF in lower section is surrounded outside Thermal barrier coating（“OTBC”）Interior thermal stress or mechanical stress concentration area, such as, around Cooling Holes, similar to the cold of Figure 20 But hole slot embodiment.In certain embodiments, EGF has tipper axis, similar to Figure 17 groove 418.

Cascaded design cavity feature（EGF）

Progressively dissipation stress in TBC layer

Figure 21 to Figure 28 more bifurcated EGF cascade plane configuration pattern（With or without lower section ESF）Control is in exposure In the heat of the blade of the operation combustion turbine engine of the hot working fluid of turbogenerator, stator blade, transition piece or other parts Crack Extension in barrier coating outer layer.During power operation, cause in the outer surface of TBC or OTBC layers thermal stress or Person's mechanical stress, for example, this is by engine thermal cycle or foreign matter（“FO”）Impact caused by result.Drawn when arbitrarily The stress risen high enough to when making TBC or OTBC fatigues of materials and being cracked in one or more inner polygons, with The stress, continuously bifurcated, the stress are decayed and disappeared at each continuous adjacent polygon in each groove binding site apex Dissipate.Other Crack Extension in the continuous polygons of one or more that the Crack Extension passes through, it is corresponding polygon to restriction at it It is prevented from the cross-shaped portion of one or more grooves of shape, or intersects at it with limiting one or more groove sections of peripheral hexagon When be prevented from.If crackle is not prevented from the hexagon of initial damage, the periphery six of Crack Extension to other adjoinings Side shape.The local stress that the gradual Crack Extension entered by summit in more bifurcated groove sections in downstream makes dissipates and decay.Once The stress of extension is less than the fatigue strength of local T BC or OTBC material, then crackle is prevented from.So, thermal barrier coating （“TBC”）In the minimal surface area that limits of the bifurcated EGF form that is limited in the outer surface by OTBC layers of Crack Damage.Such as Fruit crackle causes OTBC surfaces to be peeled off, then the remaining TBC material below crackle provides the guarantor to turbine components lower substrate Shield.Vertically-aligned EGF and ESF combination improves the holding of the remaining TBC material below crackle, such as previously herein retouches State.

The different multilayer of material and the TBC of classification constructions

As previously discussed, the TBC layer of the total thermal spraying of any turbine components embodiment described herein can have Laterally cross over parts surface or the different local material properties in TBC layer thickness.It is closest as an example The TBC layer that the one or more of anchor layer individually applies can have the intensity bigger than the layer of closer member outer surface, prolong Malleability, toughness and elastic modulus material property, but higher level layer can have bigger thermal resistance and fragile material Matter.Multilayer TBC embodiments 326 are shown in Fig. 4.Alternatively, can be by optionally changing during continuous thermal spraying technique Become for forming the constituent material of TBC layer to form the TBC layer of classification construction.In certain embodiments, on TBC outer surfaces Apply calcium and magnesium aluminium silicon（“CMAS”）Or other antipollution thing sedimentaries, adhered to for contaminant restraining deposit outside TBC Surface.Undesirable accumulation of pollutants thing can change the material character of TBC layer and reduce and be moved along the air of parts surface Force boundary condition.It is coated in CMAS- resistant layers on the EGF grooves being formed in TBC layer outer surface layer and permeates the EGF grooves Embodiment in, improve air force boundary condition by forming the TBC outer surfaces of relative smooth and suppress broken in groove Bits accumulation.

For thermal barrier coating（“TBC”）Exemplary materials composition including stabilized with yttrium oxide zirconium oxide, there is pyrochlore The crystal structure oxide of the rare earth-stabilized zirconium oxide of structure, the cubic structure of rare earth-stabilized complete stability or complexity, Such as, magneto-plumbite type either perovskite or imperfect crystal structure.Other examples TBC material composition includes having high defect density Multi-element doping oxide.The example of CMAS retarding agent compositions includes alumina, oxidation yttrium-aluminium-garnet（yttrium aluminum oxide garnet）, paste deposition/infiltration high-voidage TBC material（For OTBC or LTBC compositions Identical material）And oxidation forms the porous aluminum of Woelm Alumina.

Although each embodiment comprising the teachings of the present invention, this area it have been illustrated in detail in and have described herein Technical staff be easy to imagine that out still comprising these teaching many other different embodiments.The present invention is at it using upper It is not limited to the exemplary embodiment details of construction being stated in specification or being illustrated in accompanying drawing and the structure of part.The present invention Other embodiments can be realized and can be put into practice or performed in a variety of ways.For example, each spine and groove configuration can be with Included in different form arrays, these different form arrays can also surround the circumference of particular engine application partly Change.Moreover, it will be understood that wording used herein and term are for purposes of description and should not regarded as with limit Property processed."comprising" used herein, " comprising " or " having " and its modification are intended to the article listed thereafter and its equivalent Thing and overage.Term " installation ", " connection ", " support " and " connection " and its modification, which are covered, directly or indirectly to be pacified Dress, connection, support and connection.Each term is intended to be used broadly.In addition, " connection " and " connection " is not limited to physics Either mechanical connection or connection.

Claims

A kind of 1. combustion turbine engine blade, stator blade, transition piece with the heat-insulated outer surface for exposure to burning gases Or ring segment wear parts, the part include：

Metal substrate, the metal substrate have substrate surface；

Anchor layer, the anchoring layer building is on the substrate surface；

Design surface feature（ESF）Plane configuration pattern, the design surface feature（ESF）Plane configuration pattern formed exist Protruded in the anchor layer and from the anchor layer；

The individual layer or multilayer thermal barrier coating of the either vapour deposition or solution/suspension plasma spray coating of thermal spraying （TBC）, the thermal barrier coating（TBC）With coated on the anchor layer and being attached to table in the TBC of the anchor layer Face and the TBC outer surfaces for exposure to burning gases；And

Design cavity feature（EGF）Plane configuration pattern, the design cavity feature（EGF）Plane configuration pattern be cut and shape Into in the extremely TBC outer surfaces, and penetrate the TBC layer applied before and there is groove depth,

The plane configuration pattern on the EGF style definitions correspondingly overlying summit vertically-aligned with the corresponding ESF of lower section,

At least three corresponding groove sections in the EGF patterns are focused at each corresponding overlying apex with the pattern of more bifurcateds,

So that each convergent channel section at least has the convergent channel section of two other adjoinings in each overlying apex.
2. part according to claim 1, further comprise at least one EGF penetrated in the corresponding ESF of lower section.
3. part according to claim 1, further comprise with multiple groove depths by the TBC outer surfaces with/ Or the EGF of width.
4. part according to claim 1, further comprise that there is repetition at least a portion of the TBC outer surfaces Plane configuration pattern the EGF, the EGF has the pattern density of localized variation.
5. part according to claim 1, further comprise being formed described in polygon pattern on the TBC outer surfaces EGF。
6. part according to claim 5, the thermal stress or mechanical stress concentration area that the EGF is surrounded in the TBC.
7. part according to claim 1, at least a portion of the EGF plane configurations pattern is further only included in often Three opposed slot sections that individual apex is assembled so that each convergence groove only has the adjacent channels section of two other bifurcateds.
8. part according to claim 1, the plane configuration pattern of the EGF is included in the adjoining of overlying apex convergence Triangle and/or hexagon and/or dovetail groove pattern.
9. part according to claim 1, further comprise penetrating the thermal stress in OTBC or mechanical stress concentration area EGF.
10. part according to claim 1, further comprise at least some meetings being in direct communication with one another to form succeeding vat Poly- groove section.
11. part according to claim 1, at least some in the EGF grooves section further comprise in overlying apex The discontinuous groove section assembled but do not contacted each other in the overlying apex.
12. a kind of combustion turbine engine for including part according to claim 1, the TBC layer partial outer face with The combustion path of the engine is connected for exposed to burning gases.
13. part according to claim 1, further comprise having relative to the inclined fluted shaft line in the TBC outer surfaces At least some EGF.
14. part according to claim 1, TBC layer further comprise the either vapour deposition or solution of thermal spraying/ The lower thermal barrier coating of suspending liquid plasma body spraying（LTBC）Layer segment and outer thermal barrier coating（OTBC）Layer segment, wherein, it is described EGF penetrates the OTBC layers and entered in the LTBC layers.
15. a kind of method for manufacturing combustion turbine engine blade, stator blade, transition piece or ring segment wear parts, institute State part includes with the heat-insulated outer surface for exposure to burning gases, methods described：

Combustion turbine engine blade, stator blade, transition piece or ring segment wear parts are provided, the part includes having substrate The metal substrate on surface；

Anchor layer is formed on the substrate surface；

Form design surface feature（ESF）Plane configuration pattern, the design surface feature（ESF）Plane configuration style bit Protruded in the anchor layer and from the anchor layer；

Either vapour deposition or solution/suspension plasma spray coating the individual layer or multilayer thermal boundary for applying thermal spraying apply Layer（TBC）, the thermal barrier coating（TBC）With coated on the anchor layer and being attached in the TBC of the anchor layer Surface and the TBC outer surfaces for exposure to burning gases；And

Form design cavity feature（EGF）Plane configuration pattern, the design cavity feature（EGF）Plane configuration pattern be cut And formed into the TBC outer surfaces, and penetrate the TBC layer applied before and there is groove depth,

The plane configuration pattern on the EGF style definitions correspondingly overlying summit vertically-aligned with the corresponding ESF of lower section,

At least three corresponding groove sections in the EGF patterns are focused at each corresponding overlying apex with the pattern of more bifurcateds,

So that each convergent channel section at least has the convergent channel section of two other adjoinings in each overlying apex.
16. according to the method for claim 15, further comprise forming multiple groove depths with by the TBC outer surfaces The EGF of degree and/or width plane configuration pattern.
17. according to the method for claim 15, further comprise forming the adjoining with assembling in the overlying apex Triangle and/or the EGF of hexagon and/or dovetail groove pattern plane configuration pattern.
18. a kind of be used to control in the combustion turbine engine blade of operation, stator blade, transition piece or ring segment wear parts Thermal barrier coating（TBC）The method of Crack Extension in outer layer, the part have the heat-insulated appearance for exposure to burning gases Face, methods described include：

Combustion turbine engine blade, stator blade, transition piece or ring segment wear parts are provided, the part includes having substrate The metal substrate on surface；

Anchor layer is formed on the substrate surface；

Form design surface feature（ESF）Plane configuration pattern, the design surface feature（ESF）Plane configuration style bit Protruded in the anchor layer and from the anchor layer；

Either vapour deposition or solution/suspension plasma spray coating the individual layer or multilayer thermal boundary for applying thermal spraying apply Layer（TBC）, the thermal barrier coating（TBC）With coated on the anchor layer and being attached in the TBC of the anchor layer Surface and the TBC outer surfaces for exposure to burning gases；And

Form design cavity feature（EGF）Plane configuration pattern, the design cavity feature（EGF）Plane configuration pattern be cut And formed into the TBC outer surfaces, and penetrate the TBC layer applied before and there is groove depth,

The plane configuration pattern on the EGF style definitions correspondingly overlying summit vertically-aligned with the corresponding ESF of lower section,

At least three corresponding groove sections in the EGF patterns are focused at each corresponding overlying apex with the pattern of more bifurcateds,

So that each convergent channel section at least has the convergent channel section of two other adjoinings in each overlying apex；

The engine is operated, so as to cause thermal stress or mechanical stress in the TBC layer during engine thermal cycle, Or causing mechanical stress in the TBC layer by foreign matter impact, the stress caused by any one produces in the TBC to be split Line；And

In one or more of the crackle and the EGF or ESF rubber, the crackle is prevented in the TBC Extension.
19. according to the method for claim 18, further comprise making the institute between the member outer surface and the crackle A part for TBC layer and the isolation of components are stated, so as to leave the intact part of the TBC layer on the substrate.
20. according to the method for claim 18, further comprise making the institute between the member outer surface and the crackle A part for TBC layer and the isolation of components are stated, so as to leave the intact part of the TBC layer on the substrate.